WO2003091558A2 - Procede et dispositif de controle de combustion - Google Patents

Procede et dispositif de controle de combustion Download PDF

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Publication number
WO2003091558A2
WO2003091558A2 PCT/US2003/012578 US0312578W WO03091558A2 WO 2003091558 A2 WO2003091558 A2 WO 2003091558A2 US 0312578 W US0312578 W US 0312578W WO 03091558 A2 WO03091558 A2 WO 03091558A2
Authority
WO
WIPO (PCT)
Prior art keywords
combustion
accordance
tube
energy
operatively coupled
Prior art date
Application number
PCT/US2003/012578
Other languages
English (en)
Other versions
WO2003091558A3 (fr
Inventor
Stephen C. Jacobsen
Marc Olivier
Clark C. Davis
Original Assignee
Sarcos Investments Lc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Sarcos Investments Lc filed Critical Sarcos Investments Lc
Priority to EP03728498.1A priority Critical patent/EP1488087B1/fr
Priority to JP2003588069A priority patent/JP2005524017A/ja
Priority to AU2003234189A priority patent/AU2003234189A1/en
Publication of WO2003091558A2 publication Critical patent/WO2003091558A2/fr
Publication of WO2003091558A3 publication Critical patent/WO2003091558A3/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K5/00—Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan
    • F02K5/02—Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan the engine being of the reciprocating-piston type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01B—MACHINES OR ENGINES, IN GENERAL OR OF POSITIVE-DISPLACEMENT TYPE, e.g. STEAM ENGINES
    • F01B11/00—Reciprocating-piston machines or engines without rotary main shaft, e.g. of free-piston type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B75/00—Other engines
    • F02B75/28—Engines with two or more pistons reciprocating within same cylinder or within essentially coaxial cylinders
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C5/00—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
    • F02C5/06—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the working fluid being generated in an internal-combustion gas generated of the positive-displacement type having essentially no mechanical power output
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C99/00—Subject-matter not provided for in other groups of this subclass
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R7/00—Intermittent or explosive combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B75/00—Other engines
    • F02B75/02—Engines characterised by their cycles, e.g. six-stroke
    • F02B2075/022—Engines characterised by their cycles, e.g. six-stroke having less than six strokes per cycle
    • F02B2075/025—Engines characterised by their cycles, e.g. six-stroke having less than six strokes per cycle two
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B75/00—Other engines
    • F02B75/02—Engines characterised by their cycles, e.g. six-stroke
    • F02B2075/022—Engines characterised by their cycles, e.g. six-stroke having less than six strokes per cycle
    • F02B2075/027—Engines characterised by their cycles, e.g. six-stroke having less than six strokes per cycle four
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/03001—Miniaturized combustion devices using fluid fuels

Definitions

  • the response speed, or bandwidth, of a power source within a mechanical system is an indication of how quickly the energy produced by the source can be accessed by an application.
  • An example of a rapid response, or high bandwidth, power system is a hydraulic pressure system.
  • energy from any number of sources can be used to pressurize hydraulic fluid and store the pressurized fluid in an accumulator.
  • the energy contained in the pressurized fluid can be accessed almost instantaneously by opening a valve, often a servo-valve, in the system and releasing the fluid to perform some kind of work, such as extending or retracting a hydraulic actuator.
  • the response time of this type of hydraulic system is very rapid, on the order of a few milliseconds or less.
  • the accelerator on a vehicle equipped with an internal combustion engine controls the rotational speed of the engine, measured in revolutions per minute ("rpms").
  • rpms revolutions per minute
  • the accelerator is activated and the engine increases its rotational speed accordingly.
  • the engine cannot reach the desired change in a very rapid fashion due to inertial forces internal to the engine and the nature of the combustion process.
  • the maximum rotational output of an engine is 7000 ⁇ ms, then the time it takes for the engine to go from 0 to 7000 rpms is a measure of the response time of the engine, which can be a few seconds or more.
  • a hydraulic cylinder can be actuated in a matter of milliseconds or less, and can be operated in a rapid cycle without compromising its fast response time.
  • heavy earth moving equipment such as backhoes and front-end loaders, which utilize the hydraulic pressure system discussed above.
  • Heavy equipment is generally powered by an internal combustion engine, usually a diesel engine, which supplies ample power for the operation of the equipment, but is incapable of meeting the energy response requirements of the various components.
  • an internal combustion engine usually a diesel engine
  • the heavy equipment is capable of producing great force with very accurate control.
  • this versatility comes at a cost.
  • the present invention provides such a device and includes a combustion chamber having an extinguishing section, an ignition section, and a combustion 4 section intermediate the extinguishing section and the igniter section.
  • An igniter can be operatively coupled to the combustion chamber at the ignition see ⁇ on and a first supply system and a second supply system can be operatively coupled to the combustion chamber at the extinguishing section, the first supply system configured to supply fuel to the combustion chamber, the second supply system configured to supply an oxidizer to the combustion chamber, the fuel and oxidizer being configured to combine and form a combustible mixture.
  • the combustion chamber can be configured to provide for the combustible mixture to fill the combustion chamber from the extinguishing section toward the ignition section and to be ignited by the igniter adjacent the ignition section, wherein combustion proceeds through the combustion section from the ignition section toward the extinguishing section and then extinguishes.
  • At least one energy extraction device can be operatively coupled to the combustion chamber to extract energy from combustion of the combustible mixture.
  • the system provides for combustion to proceed through the combustion section from the ignition section toward the extinguishing section at a supersonic combustion rate.
  • An inside surface of the combustion chamber can include surface irregularities to promote turbulent flow of the combustible material through the combustion chamber to thereby increase a combustion rate of the combustible material.
  • the at least one energy extraction device can be operatively coupled to a side of the combustion chamber.
  • At least one energy extraction device is operatively coupled to an end of the combustion chamber.
  • the system includes a plurality of combustion chambers, wherein the at least one energy extraction device can be operatively coupled to the plurality of combustion chambers to extract energy from combustion of the combustible mixture in the plurality of combustion chambers.
  • the system includes a combustion control system, operatively coupled to the plurality of combustion chambers to selectively operate each of the plurality of combustion chambers.
  • the system includes a plurality of energy release ports, formed in a side of the combustion chamber to direct the energy from combustion of the combustible mixture to the at least one energy extraction device.
  • the energy extraction device includes a piston, operatively coupled to the combustion chamber to be driven by energy from combustion of the combustible mixture.
  • the piston is operatively coupled to a power device, the power device being selected from the group consisting of an electric generator, a fluid pump, a hydraulic pump, a pneumatic pump, and a mechanical transducer.
  • the energy extraction device is selected from the group consisting of a turbine, a thrust nozzle, and a pressure chamber.
  • the system includes a flow restriction device, operatively coupled to the combustion chamber to restrict a rate at which the fuel and oxidizer enter the combustion chamber.
  • the system includes a third supply system, operatively coupled to the combustion chamber to introduce into the combustion chamber a buffer material.
  • the combustion chamber can be configured to provide for the combustible mixture and the buffer material to simultaneously fill the chamber in a stratified condition.
  • the system includes an annular inlet port, operatively coupled intermediate the third supply system and the combustion chamber to fill the combustion chamber with the buffer material along an annular path adjacent an inside diameter of the combustion chamber.
  • a ratio of a length of the combustion chamber to an inside diameter of the combustion tube is greater than 5:1.
  • a length of the combustion chamber is less than 15 cm.
  • a combustion device including an elongate combustion tube having i) an 6 inlet section including an inlet for combustible material; and ii) an ignition section, including an igniter displaced along a length of the tube from the inlet section to ignite the combustible material; and at least one energy extraction device, operatively coupled to the combustion tube, configured to extract energy from combustion of the combustible mixture.
  • a combustion device including an elongate combustion tube having an inlet section and an ignition section displaced along a length of the tube from the inlet section, to receive and combust a combustible material; an igniter, operatively coupled to the combustion tube at the ignition section, to ignite the combustible material; a primary energy extraction device, operatively coupled to the combustion tube, driven by combustion of the combustible material to extract a greater amount of energy over a longer period of time; and a secondary energy extraction device, operatively coupled to the combustion tube, driven by combustion of the combustible material to extract a lesser amount of energy over a shorter period of time, as compared to the primary energy extraction device.
  • FIG. 1 is a schematic view of a controllable combustion device in accordance with an embodiment of the present invention
  • FIG. 1 A is an end sectional view of a combustion chamber or tube in accordance with an embodiment of the present invention
  • FIG. IB is a schematic view of an alternate embodiment of the device illustrated in FIG. 1 ;
  • FIG. 1C is a schematic view of an alternate embodiment of the device illustrated in FIG. 1 ;
  • FIG. ID is a schematic view of an alternate embodiment of the device illustrated in FIG. 1 : 7
  • FIG. IE is a schematic view of an alternate embodiment of the device illustrated in FIG. 1 ;
  • FIG. IF is a schematic view of an alternate embodiment of the device illustrated in FIG. 1 ;
  • FIG. 1G is a schematic view of an alternate embodiment of the device illustrated in FIG. 1;
  • FIG. 2 is a schematic view of another embodiment of the present invention.
  • FIG. 3 A is a side schematic view of another embodiment of the present invention.
  • FIG. 3B is an alternate side schematic view of the embodiment of the present invention illustrated in FIG. 3 A;
  • FIG. 3C is a top schematic view of the embodiment of the present invention illustrated in FIG. 3A;
  • FIG. 3D is a side schematic view of another embodiment of the present invention.
  • FIG. 3E is a side schematic view of another embodiment of the present invention.
  • FIG. 4 A is a side schematic view of another embodiment of the present invention.
  • FIG. 4B is a top schematic view of the embodiment of the present invention illustrated in FIG. 4A;
  • FIG. 5 is a schematic view of another embodiment of the present invention.
  • FIG. 6 A is a side schematic view of another embodiment of the present invention.
  • FIG. 6B is an end schematic view of the embodiment of the present invention illustrated in FIG. 6A.
  • FIG. 7 is a schematic view of an alternate embodiment of the present invention.
  • a combustion system indicated generally at 10, in accordance with the present invention is shown for providing controllable combustion of a combustible material.
  • the system 10 includes a combustion chamber or tube 12 that can include an extinguishing or inlet section 14, an ignition section 18, and a combustion section 16 intermediate the extinguishing section and the igniter section.
  • the igniter section 18 can be displace along a length of the tube from the inlet section, such that the igniter and inlet sections are separated by at least a portion of the length of the tube.
  • the ignition and inlet sections are located at opposing ends of the chamber or tube 12.
  • the positions of the ignition sections, the extinguishing or inlet section and the combustion section can be at any location along the length of the tube and can be located in any order relative to each other.
  • An igniter 20 can be operatively coupled to the combustion chamber or tube at the ignition section to facilitate ignition of a combustible material.
  • the igniter can be of any type known to those skilled in the art, including a hot filament, autocatalytic platinum, or standard spark plug.
  • the igniter can be located as illustrated in FIG. 1, or can be located anywhere along a length of the tube 12. In one embodiment, the igniter is located midway along the length of tube. In this embodiment, combustible material can proceed past the igniter to fill the length of the tube. Once the igniter is initiated, combustion proceeds away from the igniter in opposing directions toward both ends of the tube.
  • the combustion system can include a first supply system 22 and a second supply system 24, each operatively coupled to the combustion chamber or tube 12.
  • the first and second supply systems can be coupled to the tube near the extinguishing section 14, or at any location along the length of the tube.
  • the first supply system 22 can supply fuel to the combustion chamber or tube
  • the second supply system 24 can supply an oxidizer to the combustion chamber or tube. As the fuel and oxidizer fill the combustion tube, they can combine and form a combustible material. By displacing the ignition section along a length of the tube or chamber from the inlet section, the two materials can mix as they travel along the length of the tube to form a 9 combustible material prior to reaching the ignition section.
  • the first and second supply systems can also deliver any materials which form a combustible material when combined.
  • the type of fuel can be any known to those skilled in the art, such as propane, ethane, acetylene, hydrogen, etc.
  • the first and second supply systems can include means for pressurizing the first and second material.
  • the oxidizer supply is air pressurized at 100 to 150 psi and the fuel supply is also pressurized.
  • the combustion tube 12 can be formed of any material known to those skilled in the art, including steel, aluminum, high temperature metallic alloys, or high temperature micro-machinable materials such as Silicon or Silicone-Carbide or other machinable ceramics.
  • the size of the tubes can similarly vary, but in one embodiment a ratio of a length of the combustion chamber or tube to an inside diameter of the combustion tube is greater than 5:1. In another embodiment, a length of the combustion chamber or tube is less than 15 cm. In another embodiment, the diameter of the chamber or tube can range from 0.2 mm to 2 mm and a length can range from 20 mm to 150 mm.
  • the size of the combustion tube or chamber can also be in the micro range. This unique aspect of the present invention can allow the combustion device to be used in MEMS applications such as micro-sized machines for use in a variety of applications.
  • the combustion system is configured to fill the combustion chamber or tube 12 with a combustible material from the extinguishing section 14, through the combustion section 16, toward the ignition section 18 and to the igniter 20.
  • a combustible material from the extinguishing section 14, through the combustion section 16, toward the ignition section 18 and to the igniter 20.
  • the combustible material reaches the igniter 20, it is ignited, after which combustion proceeds, as shown by flame front 26, from the ignition section 18, through the combustion section 16, toward the extinguishing section 14, at which time combustion is extinguished as the fuel is substantially, completely consumed.
  • combustion byproducts are formed, they can be released from the tube adjacent the ignition section, or at any location along the length of the tube.
  • the locations of the various sections of the tubes as described herein are for exemplary purposes only. It is to be understood that the various sections can be located anywhere along the length of the tube and in any configuration relative to one another.
  • the present invention can provide a system for alternately filling the tube with a combustible material from the extinguishing to the 10 ignition section and combusting the material from the ignition section to the extinguishing section.
  • the combustion/filling cycle can be controlled through various means, discussed in more detail below, to provide very rapid combustion rates, very high combustion/filling cycle rates, and very flexible combustion profiles.
  • First and second valves 30 and 31, respectively, can be included in the first and second supply systems to control the inlet of materials to aid in controlling combustion rates and combustion/fill cycles.
  • the valves can be of any type known to those skilled in the art such as high speed fuel injector valves, or check valves, such as poppet or reed valves.
  • the valves can be passively or actively controlled, as discussed in more detail below.
  • the combustion system can be configured such that combustion proceeds through the tube or chamber 12 at a supersonic combustion rate. Increasing the combustion rate of the combustible material can be accomplished in many ways. The pressure and temperature of the combustible can both be adjusted to control the combustion rate. Also, as shown in FIG. 1 A, an inside surface of the combustion chamber or tube 12' can be formed with surface irregularities 11 which disrupt the flow of the combustible material along the inside surface of the combustion chamber or tube. The surface irregularities can be of any shape or size, and can extend lengthwise along the combustion chamber or tube and at various points along a cross section of the chamber or tube.
  • the disruption caused by the irregularities can create turbulent flow of the material, which can increase the rate at which the material combusts.
  • typical internal combustion engines bum combustible material (typically gasoline and air) at a rate in the range of 10-20 m/sec. It has been found that one embodiment of the present invention can combust materials at speeds considerably higher than 300 m/sec, a much faster rate of combustion. By increasing the combustion rate of the material, a very high mass of the combustible material can be burned per unit time, resulting in higher power output. Also, a cleaner combustion can be realized, resulting in less pollutants contained in combustion by-products.
  • An energy extraction device 32 advantageously can be operatively coupled to the combustion chamber or tube to extract energy from combustion of the combustible mixture. As the combustible material combusts, pressure and heat are produced which exert a force on the energy extraction device. The energy extraction device can then transfer this energy to a power source 34. As shown in FIG. 1, the 11 energy extraction device 32 can include a piston 33, or piston/cylinder. The combustion of the combustible materials can act on the piston 33 to move the piston in the cylinder. Movement of the piston 33 can be used by the energy extraction device, such as to drive hydraulics, pneumatics, or rotational or linear mechanical devices, etc.
  • the energy extraction device can include other devices, including, but not limited to, a turbine, a thrust nozzle, a pressure chamber or tube, a shape memory alloy heater, a diaphragm, and a flexure valve.
  • the combustion chamber or tube is used to provide heat for an energy extraction device, such as a heat exchanger, a Stirling engine, or a phase change device.
  • the power source 34 can include other sources, including, but not limited to, an electric generator, a fluid pump, a resonant pump, and a resonant electrical supply. Any device which can benefit from converting energy extracted by the energy extraction device can be used as a power source.
  • a flow restriction device 36 can be operatively coupled to the combustion chamber or tube to restrict a rate at which the fuel and oxidizer or combustible material enter the combustion chamber or tube.
  • the flow restriction device can be located near the extinguishing section 14, but can alternately be located anywhere along the length of the chamber or tube 12.
  • the flow restriction device can be used to assist in controlling the rate at which materials enter the chamber or tube.
  • the flow restriction device can be passively or actively controlled. In this manner, combustion rates and fill/combust cycles can be controlled to achieve optimal operation.
  • the flow restriction device can be of any type known to those skilled in the art, such as a reed valve or a poppet valve.
  • An exhaust outlet 37 can be located near the end of the piston 33 to exhaust combustion byproducts.
  • the side of the piston which can ordinarily seal the exhaust port, clears the exhaust and allows the exhaust to exit the combustion chamber or tube.
  • the exhaust is forced out the exhaust port.
  • the exhaust port can also be controlled via valves, as is known in the art.
  • the present invention thereby provides a revolutionary class of actuators tailored to enable the use of a combustion device to provide high bandwidth, low-pollutant power sources for a variety of applications.
  • Some applications that can benefit from such a device include wearable, and non- 12 wearable, energetically autonomous machines such as: exoskeletons for human performance augmentation, legged robots, and other ambulatory systems that require servo-level force control with minimal weight requirements.
  • These compact actuators can be suitable for use with any application that requires a high bandwidth, energetically autonomous power supply.
  • one embodiment of the power source 34 can be a fluid pump or compressor.
  • a fluid 38 can be provided in a reservoir 39 by a low pressure supply input 40.
  • the energy extraction device 34 can extract energy from combustion of the combustible material and transfer the energy to a small piston 44.
  • the small piston 44 is then driven toward the low pressure supply input and seals the input upon contact.
  • the small piston pressurizes the fluid 38 and forces the pressurized fluid out high pressure outlet 42.
  • High pressure output 42 can then be sealed and the small piston returned to its original location. In this manner, energy from cyclic combustion in the combustion chamber or tube can be converted to pressurized fluid, which can be used to perform useful work.
  • the fluid 38 can be compressible or incompressible and can be used, for instance for a pneumatic device or a hydraulic device.
  • the low pressure input and high pressure output can include valves (not shown) which control the input and output of fluid.
  • the valves can be any kind known to those skilled in the art, including poppet valves or reed valves.
  • the fluid pump can itself be of any type known to those skilled in the art, the embodiment illustrated in FIG. IB being only for exemplary purposes.
  • the power source 34 can also be an electric generator.
  • the energy extraction device 32 extracts energy from combustion of the combustible material
  • relative motion of the energy extraction device is translated into relative motion of a stator and plunger assembly in the electric generator.
  • a rod 46 can be fitted with magnets (not shown) which pass through a coil 48 in response to motion of the energy extraction device 32.
  • the configuration of the magnet and coil can be reversed, and the coil can pass through a magnetic field instead.
  • the motion of the rod in response to motion of the extraction device creates electricity which can be used to perform useful work.
  • the linear motion of the piston 32 can also be translated into rotary motion for use in a conventional rotary electric generator.
  • the power source 34 can also be a mechanical transducer.
  • an actuator 70 can be coupled to the piston 32.
  • linear motion is converted into rotational motion as the actuator contacts cogs 72 on a ratcheting wheel 74.
  • a retainer 76 can prevent the wheel from rotating back to its original position.
  • This configuration can be used to convert the linear cycle of the piston 32 into discrete rotational motion.
  • the mechanical transducer can be of any type known to those skilled in the art.
  • the energy extraction device can be of any type known to those in the art.
  • the energy extraction device 32a is a thrust nozzle. As combustion produces pressure, the pressurized material flows into the thrust nozzle, where its exit is restricted. A corresponding reaction force is applied to the tube or chamber.
  • the energy extraction device can be a pressure chamber 32b.
  • the pressure produced by combustion of the combustible material is stored in the pressure chamber to be released from exit 80.
  • the energy extraction device can be a turbine 32c. As pressure produced by combustion of the combustible material passes around the turbine, the turbine generates rotational energy which can be extracted by a rotational power source (not shown) at shaft 82.
  • a combustion system lOd can include a plurality of energy extraction devices 32 operatively coupled to the combustion chamber or tube 12.
  • the plurality of energy extraction devices can be coupled to a side of the combustion chamber or tube.
  • a plurality of ports 48 can be formed along the length of the combustion chamber or tube for directing combustion of the combustible material to the energy extraction devices 32.
  • each energy extraction device is successively activated.
  • the state as shown in FIG. 2 illustrates a first energy extraction device 32a having already been activated as the flame front has passed a point of coupling.
  • the combustion system lOd can be similar to that described above, and can include all of the features and advantages. Combustion byproducts can be exhausted through one main exhaust port or can be exhausted through individual exhaust ports associated with each energy extraction device.
  • a combustion system lOe can include a plurality of combustion chambers or tubes 12 operatively coupled to one or more 14 energy extraction devices 32.
  • Longitudinal axes of the plurality of combustion chamber or tubes 12 can be oriented orthogonally with respect to a longitudinal axis of the energy extraction device 32.
  • Lateral ports 48 can be positioned along the length of the combustion chambers or tubs 12 to allow energy from combustion of the combustible material to operate the energy extraction device. All of the combustion tubes can be operated simultaneously to provide energy for the energy extraction device, or the tubes can be selectively operated to employ lesser tubes at one time, depending on the desired amount of energy.
  • the combustion tubes can be selectively operated as a group or in individual firing patterns to obtain the desired amount energy.
  • the plurality of combustion tubes 12 can be selectively operated by use of a combustion control system 50.
  • the combustion control system can consist of a master control unit 51 which can be any type of controller known to those skilled in the art, such as a traditional computer with control software.
  • a series of ignition control leads 52 in operational communication with each of igniters 20 can control the extent or timing of igniter activity in each tube 12.
  • Each tube can be fitted with its own control valve 55 which controls how much, if any, combustible material is allowed to enter the tube.
  • Each tube can have one or more control valves that control the amount of combustible material that enters the tube.
  • each tube can also be fitted with two valves, one of each controlling the inlet of fuel, oxidizer or other material.
  • a series of valve control leads 54 can be in operational communication with the master controller to selectively operate each valve.
  • combustion in each of the tubes 12 can be independently controlled.
  • the control unit can be used to fire a number of tubes at one time, and fire the remaining tubes at a later time.
  • Selectively controlling the combustion of the combustion tubes can be useful, for instance, when only a fraction of the power generated by all tubes is required at any one time.
  • Selectively controlling the combustion of the combustion tubes can also be useful in situations where the combustion cycle rate of one tube is limited and it is desired to operate the energy extraction device at a faster cycle. In such a case, some of the tubes could be operated at one frequency, with others of the tubes 180° out of phase with the other tubes. Such a configuration could operate the energy extraction device at twice the cycle rate of the tubes. 15 Referring to FIG.
  • FIG. 3D an alternate configuration of a combustion system lOf with an energy extraction device 32 coupled to ends of a plurality of tubes 12.
  • the tubes can be oriented orthogonally with respect to the energy extraction device in a stacked configuration.
  • the tubes could, for instance, be mounted in a manifold, although any other mounting assembly can be used. In this manner, combustion sequences could be even further varied by, for example, simultaneously firing all of the tubes in one row, then firing the tubes in another row, etc.
  • a plurality of combustion tubes 12 can be disposed in an array, each of the combustion chambers or tubes operatively coupled to an energy extraction device 32 and power device 34.
  • the combustion control system 51 can selectively operate the combustion tubes or chambers to produce a desired output.
  • the power devices can be electric generators, similar to the embodiment shown in FIG. 1C.
  • the energy extraction devices and power devices can be of any type known to those in the art.
  • the tubes can be, for instance, selectively controlled in response to an energy demand by a secondary system (not shown).
  • the system in FIG. 3E can be coupled to a system that requires electricity at variable levels.
  • One or more tubes can be selectively operated to supply the electricity to power the secondary device.
  • another combustion system lOg can include a curved and/or spiral shaped combustion tube 12b with one or more ports 48 coupled to one or more energy extraction device 32.
  • the curved or spiral shaped combustion tube 12b allows the combustion tube to more closely match the shape of the energy extraction device, such as a circular shape of the piston/cylinder.
  • the curved or spiral shape allows the use of a longer combustion tube.
  • the energy outlet ports 48 can release energy from combustion of the combustible material into contact with the energy extraction device.
  • the spiral shape of the combustion tube can have a larger radius near an outside diameter of the energy extraction device, and a smaller radius near the igniter 20.
  • the energy release ports release energy from combustion of the combustible material downward, into the cylinder housing the energy extraction device.
  • exhaust and/or flow restriction ports or valves can also be used with this embodiment, as discussed in other embodiments.
  • another combustion system lOh includes combustion tubes 12 oriented lengthwise with respect to the energy extraction device, or with the 16 longitudinal axis of the combustion tubes parallel to the longitudinal axis of the energy extraction device. Energy produced from combustion of the combustible material is released through ends of the combustion tubes near the ignition sections 18 directly towards the energy extraction device. It is believed that directing the energy of the combustion directly towards the energy extraction device reduces flow losses.
  • a combustion system can employ a controller system, similar to that shown in FIG. 3C, to selectively operate the tubes.
  • another combustion system lOi can include a third supply system 60 operatively coupled to the combustion chamber or tube 12 to introduce into the chamber or tube a buffer material.
  • the buffer material can be any material that is not readily combustible in the present tube environment.
  • the buffer material can be air, which is not readily combustible in the tube without being mixed with a fuel.
  • the buffer material can also be the same material as the oxidizer, or the fuel when not mixed with an oxidizer.
  • the third supply system can be coupled to the combustion chamber or tube by an annular inlet port 62. Of course, any coupling of the third supply system and the tube known to those skilled in the art could be used as well.
  • the combustible material and buffer material can enter the tube in a stratified condition.
  • a buffer layer 64 of the buffer material can be formed around the combustible material as the materials progress along the tube.
  • This stratified condition is advantageous in that the buffer layer can thermally isolate the combustible material from an inside wall of the tube to prevent autoignition of the combustible material due to heat from the wall.
  • the buffer layer can also be advantageous in that it may reduce flame quenching by restricting heat loss through the wall of the chamber or tube and by restricting interaction between reactive radicals and the wall of the tube. By reducing autoignition and flame quenching, the rate and timing of combustion can be more accurately controlled.
  • the stratified condition can also be created by using additional, buffer, material from the first supply system, without the need for a third supply system.
  • the combustion system lOj can include primary and secondary energy extraction devices 66 and 68.
  • the primary energy extraction device 66 is operatively coupled to the combustion tube to be driven by combustion of the combustible material.
  • the primary energy extraction device can be configured to extract a greater 17 amount of energy over a longer period of time.
  • the 66 can include a piston movably disposed in a cylinder and operatively coupled to a rotatable member by a pivoting arm to convert reciprocal linear motion of the piston to rotational movement of the rotatable member.
  • the primary energy extraction device 66, or the rotational member can be configured to extract a greater amount of energy, but over a longer period of time.
  • the secondary energy extraction device 68 also is operatively coupled to the combustion tube to be driven by combustion of the combustible material. The secondary energy extraction device can be configured to extract a lesser amount of energy over a shorter period of time.
  • the secondary energy extraction device 68 can extract a smaller amount of energy quickly, before the primary energy extraction device 66 extracts a larger amount of energy. Therefore, the combustion system lOj can be configured for a primary purpose using the primary energy extraction device 66, while simultaneously providing energy for a secondary purpose using the secondary extraction device 68.
  • the primary energy extraction device 66 can be a reciprocating piston and the secondary energy extraction device 68 can be a fluid pump similar to the embodiments discussed above.
  • the primary and secondary extraction devices can take the form of any of the embodiments previously discussed, such as electric generators, etc.
  • the present invention thus provides a secondary energy extraction device that can rapidly extract a portion of the energy from combustion of the combustible material before a significant portion of the energy is lost to heat.
  • This "parasitic" secondary energy extraction device can be operated at very fast bandwidths due to its smaller size and lower rate.
  • a parasitic energy extraction device could be operatively coupled to a combustion system configured for lower bandwidth performance, such as driving a reciprocating engine, and yet be, itself, driven at a high bandwidth.
  • an electric generator or hydraulic pump which might require high bandwidth response to drive a particular application upon immediate demand.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
  • Portable Nailing Machines And Staplers (AREA)

Abstract

L'invention porte sur u procédé et un dispositif de contrôle de la combustion d'un matériau combustible comportant: (i) un dispositif de combustion (10) consistant en un tube (12) allongé présentant une section d'introduction (14) munie d'un orifice d'introduction du matériau combustible; (ii) une section d'allumage (16) munie d'un allumeur (20) situé dans le tube à distance de l'orifice d'introduction et servant enflammer le matériau combustible; et (iii) au moins un dispositif d'extraction d'énergie (32) fonctionnellement relié au tube (12) et servant à extraire l'énergie de combustion du mélange combustible.
PCT/US2003/012578 2002-04-23 2003-04-23 Procede et dispositif de controle de combustion WO2003091558A2 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP03728498.1A EP1488087B1 (fr) 2002-04-23 2003-04-23 Procede et dispositif de controle de combustion
JP2003588069A JP2005524017A (ja) 2002-04-23 2003-04-23 制御可能な燃焼方法及び装置
AU2003234189A AU2003234189A1 (en) 2002-04-23 2003-04-23 Controllable combustion method and device

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US10/128,988 US6938588B2 (en) 1999-11-12 2002-04-23 Controllable combustion method and device
US10/128,988 2002-04-23

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WO2003091558A2 true WO2003091558A2 (fr) 2003-11-06
WO2003091558A3 WO2003091558A3 (fr) 2004-04-29

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2008522101A (ja) * 2004-12-02 2008-06-26 サーコス・インヴェストメンツ・エルシー 動的質量移送迅速応答動力変換システム

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060156727A1 (en) * 1999-11-12 2006-07-20 Jacobsen Stephen C Method and apparatus for phase change driven actuator
JP4633402B2 (ja) * 2004-08-20 2011-02-16 ダイセル化学工業株式会社 回転体の回転装置
US7438030B1 (en) 2005-08-26 2008-10-21 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Actuator operated microvalves
KR20100071087A (ko) * 2007-10-04 2010-06-28 시리트 엘엘씨 전자기 엔진
US9359973B2 (en) * 2010-06-15 2016-06-07 Exponential Technologies, Inc. Multitube valveless pulse detonation engine
US8881500B2 (en) * 2010-08-31 2014-11-11 General Electric Company Duplex tab obstacles for enhancement of deflagration-to-detonation transition
BR112013010886A2 (pt) 2010-11-05 2016-08-02 Thermochem Recovery Int Inc sistema de circulação de sólidos e processo para captura e conversão de sólidos reativos
US10208599B2 (en) * 2011-05-13 2019-02-19 Brian Davis Heat engine with linear actuators
FR2975468B1 (fr) 2011-05-16 2016-01-01 Mbda France Moteur a onde de detonation continue et engin volant pourvu d'un tel moteur
WO2013049368A1 (fr) 2011-09-27 2013-04-04 Thermochem Recovery International, Inc. Système et procédé pour l'épuration de gaz de synthèse
GB2502582B (en) * 2012-05-31 2017-09-27 Abu Al-Rubb Khalil An internal combustion engine and method of operating an internal combustion engine
EP2906795B1 (fr) * 2012-10-12 2019-05-01 King Abdullah University Of Science And Technology Moteur à détonations
WO2015143362A1 (fr) * 2014-03-20 2015-09-24 Board Of Regents, The University Of Texas System Systèmes et procédés de production de puissance utilisant une source de combustion
US10450943B2 (en) * 2014-03-27 2019-10-22 The Trustees Of Princeton University Otto and diesel cycles employing spinning gas
FR3037384B1 (fr) * 2015-06-11 2017-06-23 Turbomeca Module de chambre de combustion cvc de turbomachine comportant une prechambre de combustion
EP4215289A1 (fr) 2016-02-16 2023-07-26 ThermoChem Recovery International, Inc. Système et procédé de génération de produit gazeux intégré en énergie à deux étages
ES2923073T3 (es) 2016-03-25 2022-09-22 Thermochem Recovery Int Inc Sistema de generación de producto gaseoso integrada en energía de tres fases
US10364398B2 (en) 2016-08-30 2019-07-30 Thermochem Recovery International, Inc. Method of producing product gas from multiple carbonaceous feedstock streams mixed with a reduced-pressure mixing gas
US9920926B1 (en) 2017-07-10 2018-03-20 Thermochem Recovery International, Inc. Pulse combustion heat exchanger system and method
FR3069287B1 (fr) * 2017-07-21 2021-07-02 Safran Chambre de combustion pour turbomachine a detonation rotative et turbomachine a detonation rotative
US10099200B1 (en) 2017-10-24 2018-10-16 Thermochem Recovery International, Inc. Liquid fuel production system having parallel product gas generation
US10830562B2 (en) * 2019-04-14 2020-11-10 Hamilton Sundstrand Corporation Wearable power modules with distributed energy storage systems
US11555157B2 (en) 2020-03-10 2023-01-17 Thermochem Recovery International, Inc. System and method for liquid fuel production from carbonaceous materials using recycled conditioned syngas
US20210372324A1 (en) * 2020-05-29 2021-12-02 Purdue Research Foundation Detonation Engine having a Discontinuous Detonation Chamber
US11466223B2 (en) 2020-09-04 2022-10-11 Thermochem Recovery International, Inc. Two-stage syngas production with separate char and product gas inputs into the second stage

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003004876A1 (fr) 2001-07-05 2003-01-16 Sarcos L.C. Dispositif de conversion d'energie a reponse rapide

Family Cites Families (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1788140A (en) * 1928-04-19 1931-01-06 Packard Motor Car Co Internal-combustion engine
NL31790C (fr) 1930-04-23
US1914940A (en) * 1930-05-15 1933-06-20 Wright Aeronautical Corp Cooling of spark plugs and the like
US2581669A (en) 1945-04-13 1952-01-08 Nina K Guercken Gas turbine power plant with tank supplied by long conduit having volume over six times that of the intermittent combustion gas generator
US2573697A (en) 1945-07-30 1951-11-06 James Y Dunbar Multitube mosaic reso-jet motor
US2525782A (en) 1945-08-02 1950-10-17 James Y Dunbar Shock wave trap for multiple combustion chamber reso-jet motors
US2647365A (en) 1946-02-19 1953-08-04 Elman B Myers Reso-jet motor
US2539535A (en) 1946-03-16 1951-01-30 Bell Telephone Labor Inc Source of electrical energy
US2549464A (en) 1947-10-29 1951-04-17 Bell Telephone Labor Inc Electric power source
US2838102A (en) 1954-08-28 1958-06-10 Junkers & Co Pulse jet burner system
US3093962A (en) 1957-03-11 1963-06-18 Eugene M Gluhareff Valveless jet engine with inertia tube
GB984949A (en) * 1962-07-25 1965-03-03 Daimler Benz Ag Improvements relating to rotary piston-internal combustion engines
FR1447143A (fr) 1964-02-08 1966-07-29 Inst Francais Du Petrole Procédé et dispositif d'obtention d'une succession de zones à températures différentes dans un générateur d'électricité par magnétohydrodynamique
US3545211A (en) 1967-01-27 1970-12-08 Marquardt Corp Resonant pulse rocket
US3644069A (en) * 1969-08-11 1972-02-22 George R Stewart Rotary engine construction
US3854380A (en) * 1972-06-23 1974-12-17 Caterpillar Tractor Co Three-way lever control for hydraulic control circuit
BE786418A (fr) * 1972-07-18 1972-11-16 Dutry Jean E Moteur a combustion interne.
US3954380A (en) 1974-09-16 1976-05-04 Alexandr Alexandrovich Valaev Method and apparatus for intermittent combustion
JPS5950850B2 (ja) * 1976-12-27 1984-12-11 日産自動車株式会社 内燃機関の吸気装置
US4907549A (en) * 1988-04-30 1990-03-13 Fuji Jukogyo Kabushiki Kaisha Scavenging system for a two-stroke-cycle engine
DE3826446A1 (de) * 1988-08-04 1990-02-08 R & D Carbon Ltd Zerstaeuberbrenner fuer fluessige brennstoffe
US5123835A (en) 1991-03-04 1992-06-23 The United States Of America As Represented By The United States Department Of Energy Pulse combustor with controllable oscillations
US5322043A (en) * 1992-08-05 1994-06-21 Shriner Robert D Spiral spin charge or sheathing system
US5302112A (en) * 1993-04-09 1994-04-12 Xothermic, Inc. Burner apparatus and method of operation thereof
DE19743060A1 (de) * 1997-09-30 1999-04-01 Bosch Gmbh Robert Verfahren zum Betrieb einer Brennkraftmaschine und Kraftstoffeinspritzsystem zur Durchführung des Verfahrens

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003004876A1 (fr) 2001-07-05 2003-01-16 Sarcos L.C. Dispositif de conversion d'energie a reponse rapide

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2008522101A (ja) * 2004-12-02 2008-06-26 サーコス・インヴェストメンツ・エルシー 動的質量移送迅速応答動力変換システム

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WO2003091558A3 (fr) 2004-04-29
JP2005524017A (ja) 2005-08-11
US20030108830A1 (en) 2003-06-12
EP1488087A4 (fr) 2011-03-16
US6938588B2 (en) 2005-09-06
AU2003234189A1 (en) 2003-11-10
AU2003234189A8 (en) 2003-11-10
EP1488087A2 (fr) 2004-12-22
EP1488087B1 (fr) 2013-05-22

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